EP2190650B1 - Herstellungsverfahren einer hohlen verbundstruktur - Google Patents

Herstellungsverfahren einer hohlen verbundstruktur Download PDF

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Publication number
EP2190650B1
EP2190650B1 EP07871181.9A EP07871181A EP2190650B1 EP 2190650 B1 EP2190650 B1 EP 2190650B1 EP 07871181 A EP07871181 A EP 07871181A EP 2190650 B1 EP2190650 B1 EP 2190650B1
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EP
European Patent Office
Prior art keywords
fiber plies
pressurizable
members
mold
pressurizable members
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP07871181.9A
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English (en)
French (fr)
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EP2190650A1 (de
Inventor
William L. Rodman
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Aerosud Technology Solutions (ptd) Ltd
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Aerosud Technology Solutions (ptd) Ltd
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Publication of EP2190650A1 publication Critical patent/EP2190650A1/de
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/549—Details of caul plates, e.g. materials or shape
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/546—Measures for feeding or distributing the matrix material in the reinforcing structure
    • B29C70/547—Measures for feeding or distributing the matrix material in the reinforcing structure using channels or porous distribution layers incorporated in or associated with the product
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/546—Measures for feeding or distributing the matrix material in the reinforcing structure
    • B29C70/548—Measures for feeding or distributing the matrix material in the reinforcing structure using distribution constructions, e.g. channels incorporated in or associated with the mould
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/24—Condition, form or state of moulded material or of the material to be shaped crosslinked or vulcanised
    • B29K2105/246—Uncured, e.g. green
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2022/00—Hollow articles

Definitions

  • the invention is generally related to producing large, complex-shaped, three-dimensional, fiber reinforced composite components and structures, such as composite components and structures where the requirements for surface finish, strength and damage tolerance are high.
  • a composite component is a term generally used to describe any part consisting of at least two constituents that are combined yet retain their physical and chemical identities.
  • One type of composite component is a particulate reinforced composite (PRC) in which particulates of a selected material are embedded or bonded into a matrix.
  • PRC particulate reinforced composite
  • An advanced composite component is a term generally used to describe fibers of high strength and modulus embedded in or bonded to a matrix, such as a resin, metal, ceramic, or carbonaceous matrix. The fibers may be continuous fibers, short fibers, or whiskers.
  • the resin type matrix may be a polymerized synthetic or a chemically modified natural resin, which may include but is not limited to thermoplastic materials such as polyvinyl, polystyrene, and polyethylene and thermosetting materials such as polyesters, epoxies, and silicones. Typically, a distinct interface or boundary is present between the fibers and the matrix material. It is appreciated that the composite component produces a combination of properties that cannot be achieved with either of the constituents acting alone.
  • a composite component is typically produced by a multi-step process that begins by laying up the fibers generally in swatches of material known as laminates or plies on an impervious surface.
  • the plies may be pre-impregnated with the matrix material or may be un-impregnated.
  • the un-impregnated fibers may be embedded or bonded in the matrix material by using injection molding, reaction injection molding (RIM), resin infusion, or other matrix embedding or bonding techniques.
  • RIM reaction injection molding
  • compaction techniques such as vacuum bagging are advantageously employed to remove voids from the fiber plies.
  • the matrix material surrounding the plies may be cured employing ovens, electron beams, ultraviolet, infrared light sources, autoclave cured. Curing may be carried out at room (i.e., ambient) or elevated temperatures.
  • One existing manufacturing process for producing large, complex-shaped, three-dimensional, fiber reinforced composite components and structures includes arranging fiber plies arranged on plaster mandrels to form the complex shape. Fiber reinforced plies are laid up and impregnated on the plaster mandrels, which have been previously varnished to seal them. The resulting structure is vacuum bagged and cured. The plaster mandrel is removed by striking it through the laid up, crumbling the plaster mandrel to leave the hollow composite component.
  • This technique is commonly used to produce structures such as complex-shaped, air conditioning ducts. This type of tooling may include locking features that hold the tool's complex shape.
  • steel, aluminum, or invar tooling materials may be used to create shapes that can be fastened or otherwise coupled together to create a mold surface for laying up the fiber plies.
  • steel, aluminum, or invar tooling materials may be used to create shapes that can be fastened or otherwise coupled together to create a mold surface for laying up the fiber plies.
  • an auxiliary power unit inlet duct for an airplane typically requires structural materials that exceed the strength requirements obtainable from the plaster mandrel techniques described above.
  • the network of smaller channels may also be provided between the vacuum bag and the fiber material, either integrally in the vacuum bag or via a separate distribution medium.
  • Resin introduced under vacuum, travels relatively quickly through the main feeder channel(s) and into the network of smaller channels. After penetrating the fiber material to reach the surface of the cores, the resin again travels relatively quickly along the cores via the grooves in the cores or the spaces provided by the rounded corners to penetrate the fiber material wrapped around and even between the cores.
  • the resin is then cured after impregnating the fiber material to form a three-dimensional, fiber reinforced composite component and structure.
  • US 5,000,990 discloses a method of manufacturing one-piece moulded composite parts using an inflatable thin-walled support and mould system.
  • the present invention relates to a method of making a composite structure, the method comprising: obtaining a plurality of pressurizable members each having sufficient rigidity for supporting fiber plies thereon in a desired shape before pressurization, the pressurizable members having an outer surface and an inner surface forming a wall that defines a volumetric region, wherein the plurality of pressurizable members are coupled together to be in fluid communication with an adjacent pressurizable member, one of the pressurizable members having an opening to permit internal pressurization of the plurality of coupled pressurizable members; arranging fiber plies on the outer surface of the pressurizable members, wherein each of the pressurizable members supports the fiber plies thereon in a desired shape before pressurization of the pressurizable members; placing the fiber plies and the pressurizable members into a mold; sealing the fiber plies within the mold to permit pressurization of the fiber plies; pressurizing an exterior surface of the fiber plies with a first pressure; and pressurizing the inner surface of the pressuri
  • a complex-shaped, three-dimensional fiber reinforced composite structure may be formed by using counteracting acting pressures applied to a structural lay-up of fiber plies.
  • the fiber plies are arranged on a pressurizable member.
  • the pressurizable member may become an integral part of the final product, or may be removed, depending on the accessibility of the member.
  • the pressurizable member is a hollow rotomolded thermoplastic member, a blow molded thermoplastic member, a superplastic formed metallic member, or a twin sheet vacuum formed member (TSVF) having an opening or vent.
  • the opening or vent allows an inner surface of the pressurizable member to be vented or pressurized such that it is expanded or inflated against the fiber plies.
  • the vented pressurizable member allows the complex-shaped, three-dimensional fiber reinforced composite structure to be produced using elevated temperature, pressure, and/or autoclave techniques.
  • pressure within the pressurizable members may be equalized as temperature rises or additional pressure may be applied, as in the use of an autoclave.
  • a number of the pressurizable members which may be of different sizes and have complex shapes, are arranged to form a large, complex-shaped lay-up surface for the fiber plies.
  • the ability to equalize the pressure in the pressurizable members allows for the production of complex-shaped, three-dimensional structures such as frames, intercostals, ribs, etc. and further permits the fiber plies to maintain their correct geometric shape.
  • FIG 1A schematically shows an autoclave system 100 having a tooling assembly or mold 102.
  • Fiber plies 104 are arranged on pressurizable members 106 and the resulting assembly 108 is placed in the mold 102.
  • the arrangement of the fiber plies 104 and the manufacturing of the pressurizable members 106 will be described in greater detail below.
  • the illustrated embodiment shows the outer surface 110 of the pressurizable members 106 as separated or spaced apart from the fiber plies 104. However during assembly, it is appreciated that the fiber plies 104 are laid up directly onto the outer surface 110 of the pressurizable members 106.
  • the mold 102 is a leak tight system having a mold body 112 optionally formed with feeder grooves or channels 114 to infuse matrix material (not shown) into or sufficiently wet the fiber plies 104.
  • the feeder grooves 114 may include main feeder grooves 116 and distribution channels 118.
  • the feeder grooves 114 may be included in the pressurizable members 106, which is an embodiment described below.
  • the mold 102 is a tightly (i.e., close tolerance) machined clamshell type mold 102.
  • a removable, stiffened peel ply 120 may be laid up or take the form as an outer layer or outer ply on the outer surface 110 of the fiber plies 104.
  • the stiffened peel ply 120 could then be peeled or otherwise separated from the fiber plies 104 after the matrix material is cured.
  • the stiffened peel ply 120 permits the matrix material associated with the feeder grooves 114 to be peeled away from fiber plies 104 during finishing operations (i.e., post matrix material cure).
  • the arrangement, volumetric flow rate, and volumetric capacity, for example, of the feeder grooves 114 may be optimized or otherwise controlled for the particular structural component being manufactured.
  • the different matrix materials may be utilized to achieve improved results.
  • the matrix material comprises a resin
  • a number of different resins may be employed based on the processing temperature, for example a polyethylene resin may be used at low temperatures, an epoxy, phenolic, or bismaleimide resing at medium temperatures, and finally a polyimide resin at higher temperatures.
  • other resins such as nylon, polyethersulfone (PES), polyetherimide (PEI), or acetal may be used to customize the fiber-reinforced structure.
  • the mold 102 further includes a caul sheet 122, a bagging film 124, and a probe 126.
  • the caul sheet 122 may be coupled to the mold body 112 to secure the fiber plies 104 and the pressurizable members 106 within the mold 102.
  • the caul sheet 122 may take the form of a sheet or plate material that is generally placed in immediate contact with the fiber plies 104 during curing to transmit normal pressure and provide a smooth surface on the finished component.
  • the caul sheet 122 takes the form of a stiffened, three ply sheet material, but may take other forms depending on the autoclave system 100 and other design considerations.
  • the bagging film 124 is sealed to various portions of the mold 102 with sealant 128. In addition, the bagging film 124 is sealed to sprues or pressure ports 130 extending from the pressurizable members 106.
  • the bagging film 124 preferably takes the form of a three ply porous breather material, but may take other forms depending on the autoclave system 100 and other design considerations.
  • the probe 126 typically operates to place the fiber plies 104 under a vacuum pressure by removing air from the mold 102. In other embodiments, however, it is appreciated that the probe 126 may operate to increase the pressure within the mold 102.
  • the bagging film 124 may also be sealed to the probe 126 using the sealant 128.
  • FIG. 1B schematically shows the autoclave system 100 having a tooling assembly or mold 102 according to another embodiment of the invention.
  • the illustrated embodiment is substantially similar to the previous embodiment so that like numbers are re-used except where there are differences.
  • the fiber plies 104 are arranged on interconnecting pressurizable members 106a and 106b within the mold 102. Again and for purposes of clarity only, the illustrated embodiment shows an outer surface 1 10 of the pressurizable members 106a, 106b as separated or spaced apart from the fiber plies 104. However during assembly, it is appreciated that the fiber plies 104 are laid up directly onto the outer surface 1 10 of the pressurizable members 106a, 106b.
  • pressurizable member 106a includes a first fluid port 107 that extends into a second fluid port 109 of pressurizable member 106b.
  • the fiber plies 104 are arranged so they do not block or interfere with the ports 107, 109.
  • an amount of sealant 111 may be located around the first fluid port 107.
  • the sealant 111 is arranged so that it does not extrude into the fiber plies 104 during pressurization.
  • Figure 2 shows a slightly different example for pressurizing the autoclave system 100 without using the bagging film 124.
  • the caul sheet 122 is sealed against the mold body 112 of the mold 102 and the sprues 130 of the pressurizable members 106. It is appreciated that other autoclave system 100 configurations and methods of sealing the mold 102 may operate in accordance with the invention, but they will not be further described herein for purposes of brevity.
  • Figure 3 shows the assembly 108 comprising the fiber plies 104 and the pressurizable members 106.
  • the pressurizable members 106 may be configured to be non-removable after the fiber plies 104 and injected or infused matrix material are cured.
  • the integration of the pressurizable members 106 with the fiber plies 104 to make the flyaway component may or may not be accomplished by using a bondable material therebetween.
  • the type of material, the size, and the weight of the pressurizable members 106 would likely have to be closely controlled for the flyway component to meet its design requirements.
  • the thickness of the pressurizable members 106 will add to the overall weight of the flyway component. If the members 106 are too thin, or if they are not made of a durable material, then the bagging details may collapse, split or explode during pressurization and curing of the assembly 108 within the mold 102 ( Figure 1 ). Additionally, the presence of the pressurizable members 106 in contact with the fiber plies 104 could affect the engineering properties of the flyway component. In addition, the strength, properties, and structural reliability of the bondable material 132 will need to be tailored for each flyway component to minimize and preferably prevent crack propagation from the bondable material 132 into the cured fiber plies 104.
  • the pressurizable members 106 are preferably blow molded, TSVF or rotomolded thermoplastic materials with pressurizable inner chambers or volumetric regions 134.
  • the pressurizable members 106 may be manufactured to have complex shapes, contours, and other features onto which the fiber plies 104 are arranged.
  • Each pressurizable member 106 preferably includes at least one opening or sprue 130 to vent the hollow pressurizable member 106 to autoclave pressure or some other pressure "P.” By pressurizing or venting the inner chamber 134, the pressurizable member 106 is urged against the un-cured fiber plies 104 to compress and sandwich the fiber plies 104 between the pressurizable member 106 and the mold 102.
  • the pressurizable member may be produced from a chemically pure titanium tube in which the titanium tube is super plastically formed to create a metal matrix composite shape.
  • the sprue 130 is used to introduce a pressure P into the chamber 134 that is greater than the autoclave pressure. After pressurizing and curing the fiber plies 104, the sprue 130 may vent gases built up in the chamber.
  • the sprue 130 may take the form of a fitting coupled to an air pump or other pressure source.
  • the pressurizing and curing of the fiber plies 104 may be accomplished by pressurizing only the chambers 134 of the pressurizable members 106, thus eliminating the need for the bagging film 124 described in Figure 1 .
  • impregnated (sometimes referred to as pre-impregnated) fiber plies 104 are arranged on the pressurizable member 106.
  • the use of impregnated fiber plies may eliminate the step of injecting or infusing matrix material into the mold 102.
  • a resin transfer molding process is used to infuse resin into the fiber plies 104 and the pressurizable members 106 are pressurized without being placed in the mold 102.
  • a plurality of pressurizable members 106 are coupled together to be in fluid communication with an adjacent pressurizable member 106 such that air, gas, or some other fluid may flow freely into one of the pressurizable members 106 and simultaneously or contemporaneously pressurize all of the pressurizable members 106 that are in fluid communication with one another.
  • the fiber plies 104 may be laid up or arranged with a 45 degree bias, which permits the pressurizable member 106 to considerably expand during the cure process.
  • the arrangement of the fiber plies 104 and the configuration of the pressurizable members 106 cooperate to ensure compression of all fiber plies 104 and thus prevent wrinkles during the cure process.
  • FIG. 4 shows an autoclave system 200 having a mold 202 comprising a mold body 212 without feeder grooves. Instead, the feeder grooves 214 are formed in the pressurizable members 206, which are configured to be removable from the fiber plies 204 after curing.
  • the autoclave system 200 in most respects, is similar to the autoclave system 100 described above, with the only difference being that the feeder grooves 214 are formed in the pressurizable members 206.
  • One purpose for forming the feeder grooves 214 in the pressurizable members 206 is to achieve a more desirable or more intricate matrix material distribution network.
  • Another purpose for forming the feeder grooves 214 in the pressurizable members 206 is to reduce some of the complexity and cost of making the mold body 212. For example, when forming the matrix material distribution network in mold body 212, it is appreciated that lay-up scheme of the fiber plies 104 should be carefully thought out.
  • Figure 5 shows an aerospace component 300, for example a drag link, which is a primary load path component that couples an engine nacelle to the rear spar of an airplane wing. As the engine creates thrust, load is directed through the nacelle, to the drag link 300, which transfers the load to the rear spar. Because a drag link 300 is hollow and includes a necked down configuration, it has not been possible to create this component using any of the known fiber-reinforced composite technologies given the space constraints and geometry of the drag link 300.
  • the drag link 300 includes an elongated body 302 with fittings 304 at each end for attaching to the nacelle and rear spar, respectively.
  • the fittings 304 are fiber-composite fittings 312 integrally formed with the elongated body 302.
  • the fittings 304 are metallic fittings 314 bonded to the elongated body 302.
  • One method of producing the drag link involves obtaining the flyway pressurizable member 310 and arranging pre-impregnated or un-irnpregnated fiber plies on the pressurizable member 310.
  • debulk cycles may be employed to compact the plies by vacuum bagging the plies at room or at a slightly elevated temperature.
  • metallic inserts may be assembled into the fiber plies.
  • the metallic inserts may take the form of removable tooling components that are pinned or secured in place to create a controlled surface or they may be metallic fittings bonded in situ. The aforementioned steps may be repeated until the uncured drag link 300 is sufficiently complete.
  • the uncured drag link 300 may be placed in a "clam shell” type mold and the pressurizable member 310 is connected to a pressure source.
  • the mold is closed and sealed.
  • the pressurizable member 310 is pressurized and subjected to curing energy, such as temperature, infrared, electron beam, ultraviolet radiation or another substantially equivalent curing process.
  • curing energy such as temperature, infrared, electron beam, ultraviolet radiation or another substantially equivalent curing process.
  • the cured drag link 300 is removed from the mold, any excess matrix material may be removed using known techniques and process, and a finish or other type of protective coating may be applied to the cured drag link 300.
  • aspects of the invention enable the manufacture of complex-shaped fiber-reinforced composite structures that otherwise could not be produced or would require substantial advanced and expensive assembly techniques.
  • aspects of the invention may allow for the manufacture of a complex-shaped fiber-reinforced composite structure having substantially reduced weight when compared to a similar metallic component, enable radical new designs and structural configurations, and may lower production costs of complex-shaped fiber-reinforced composite structures.
  • the flyaway component may be produced as a single, monolithic component or may be made in pieces or sections that are coupled together after each piece or section is pressurized and cured.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)

Claims (10)

  1. Ein Verfahren zur Herstellung einer Verbundstruktur (108), wobei das Verfahren umfasst:
    Erhalten einer Vielzahl von druckbeaufschlagbaren Elementen (106), wovon jedes eine ausreichende Steifigkeit zum darauf Abstützen von Faserlagen (104) in einer gewünschten Form vor einer Druckbeaufschlagung hat, wobei die druckbeaufschlagbaren Elemente eine Außenfläche (110) und eine Innenfläche haben, die eine einen volumetrischen Raum (134) definierende Wand bildet, wobei die Vielzahl von druckbeaufschlagbaren Elementen miteinander verbunden sind, um in Fluidverbindung mit einem benachbarten druckbeaufschlagbaren Element zu sein, wobei eines der druckbeaufschlagbaren Elemente (106) eine Öffnung (130) hat, um eine innerliche Druckbeaufschlagung der Vielzahl von druckbeaufschlagbaren Elementen zu erlauben;
    Anordnen von Faserlagen (104) auf der Außenfläche (110) der druckbeaufschlagbaren Elemente (106), wobei jedes der druckbeaufschlagbaren Elemente (106) die Faserlagen darauf in einer gewünschten Form vor einer Druckbeaufschlagung der druckbeaufschlagbaren Elemente (106) abstützt;
    Platzieren der Faserlagen (104) und der druckbeaufschlagbaren Elemente (106) in einer Form (102);
    Abdichten der Faserlagen (104) in der Form (102), um eine Druckbeaufschlagung der Faserlagen (104) zu erlauben;
    unter Druck setzen einer Außenfläche der Faserlagen (104) mit einem ersten Druck; und
    unter Druck setzen der Innenfläche der druckbeaufschlagbaren Elemente über die Öffnung (130) mit einem zweiten Druck (P), wobei der erste Druck (P) und der zweite Druck zusammenwirken, um die Faserlagen (104) zwischen der Form (102) und den druckbeaufschlagbaren Elementen (106) zu komprimieren.
  2. Das Verfahren nach Anspruch 1, wobei das Erhalten der druckbeaufschlagbaren Elemente das Erhalten der druckbeaufschlagbaren Elemente (106) aus der Gruppe bestehend aus rotationsgeformten thermoplastischen Elementen, blasgeformten thermoplastischen Elementen, superplastisch geformten metallischen Elemente und vakuumgeformten Doppelblechelementen umfasst.
  3. Das Verfahren nach Anspruch 1, wobei das Abdichten der Faserlagen (104) in der Form (102) das Abdichten einer Vakuumfolie (124) gegenüber der Form (102) und gegenüber der Öffnung (130) der druckbeaufschlagbaren Elemente (106) umfasst.
  4. Das Verfahren nach Anspruch 1, wobei das Abdichten der Faserlagen (104) in der Form (102) das Isolieren der Faserlagen (104) gegenüber einem Umgebungsdruck umfasst.
  5. Das Verfahren nach Anspruch 1, weiter das Hineingießen eines Matrixmaterials in die Faserlagen (104) umfassend, um die Faserlagen (104) in der Form (102) ausreichend zu imprägnieren.
  6. Das Verfahren nach Anspruch 5, wobei das Hineingießen des Matrixmaterials das Hineingießen eines Harzes in einer im Wesentlichen flüssigen Form umfasst.
  7. Das Verfahren nach Anspruch 1, wobei das Druckbeaufschlagen der Außenfläche der Faserlagen (104) mit dem ersten Druck das einem Vakuum Aussetzen der Außenfläche der Faserlagen (104) umfasst.
  8. Das Verfahren nach Anspruch 1, wobei das Druckbeaufschlagen der Außenfläche der Faserlagen (104) mit dem ersten Druck das einem Druck größer als eine Atmosphäre Aussetzen der Außenfläche der Faserlagen (104) umfasst.
  9. Das Verfahren nach Anspruch 1, wobei das unter Druck setzen der Innenfläche der druckbeaufschlagbaren Elemente (106) ein einem Druck größer als eine Atmosphäre Aussetzen der Innenfläche der druckbeaufschlagbaren Elemente (106) umfasst.
  10. Das Verfahren nach Anspruch 1, wobei das unter Druck setzen der Innenfläche der druckbeaufschlagbaren Elemente (106) über die Öffnung (109) ein unter Druck setzen (P) der Innenfläche der druckbeaufschlagbaren Elemente (106) durch eine Gusskanal (130) umfasst.
EP07871181.9A 2007-08-07 2007-10-18 Herstellungsverfahren einer hohlen verbundstruktur Active EP2190650B1 (de)

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US11/835,261 US8834782B2 (en) 2007-08-07 2007-08-07 Composite structures and methods of making same
PCT/US2007/081748 WO2009020466A1 (en) 2007-08-07 2007-10-18 Hollow composite structure and method of amking same

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US20090041972A1 (en) 2009-02-12
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CN102083616A (zh) 2011-06-01
EP2190650A1 (de) 2010-06-02
US8834782B2 (en) 2014-09-16

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